Swirler mount interface for gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-10088166-B2
Application number	US-201414904490-A
Country	US
Kind code	B2
Filing date	May 15, 2014
Priority date	Jul 15, 2013
Publication date	Oct 2, 2018
Grant date	Oct 2, 2018

Abstract

A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged tabs are radially displaced from the threaded section.

First claim

What is claimed is:

1. A combustor of a gas turbine engine, comprising:
a bulkhead support shell with a swirler boss, said swirler boss including a multiple of circumferentially arranged ramps extending radially from said swirler boss; and
a swirler body with a threaded section defined around a swirler longitudinal axis, said swirler body including a multiple of circumferentially arranged tabs radially displaced from said threaded section,
wherein said multiple of circumferentially arranged tabs each include a lip.

2. The combustor as recited in claim 1 , wherein said multiple of circumferentially arranged ramps are directed outward with respect to said swirler longitudinal axis.

3. The combustor as recited in claim 2 , wherein each of said multiple of circumferentially arranged ramps define a step.

4. The combustor as recited in claim 1 , wherein said multiple of circumferentially arranged tabs extend axially beyond said threaded section.

5. A method of assembling a swirler within a combustor, the method comprising:
detachably mounting a swirler to a bulkhead support shell using a threaded mount interface defined between said swirler and said bulkhead support shell; and
rotating said swirler to drive a multiple of circumferentially arranged tabs of said swirler over a structure of the bulkhead support shell configured to receive the multiple of circumferentially arranged tabs.

6. The method as recited in claim 5 , wherein the structure of the bulkhead support shell includes a multiple of circumferentially′ arranged ramps.

7. The method as recited in claim 6 , further comprising rotating the swirler to snap the multiple of circumferentially arranged tabs over the multiple of circumferentially arranged ramps, wherein each of the multiple of circumferentially arranged ramps defines a step configured to receive a respective tab.

Assignees

• United Technologies Corp

Inventors

• Drake Christopher
• Max Seth A
• Harris Meggan

Classifications

• F02C7/2365

  comprising an air supply system for the atomisation of fuel · CPC title

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title

• B23P19/04

  for assembling or disassembling parts · CPC title